CN110901898B - Aircraft gravity center limiting method and device - Google Patents
Aircraft gravity center limiting method and device Download PDFInfo
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- CN110901898B CN110901898B CN201911157157.4A CN201911157157A CN110901898B CN 110901898 B CN110901898 B CN 110901898B CN 201911157157 A CN201911157157 A CN 201911157157A CN 110901898 B CN110901898 B CN 110901898B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
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Abstract
The invention discloses a method and a device for limiting the gravity center of an aircraft. The method comprises the following steps of displaying points of an aircraft in a coordinate system, and calculating an aircraft index and an assembly industry load index, wherein the assembly industry load index comprises the following steps: and calculating the center of gravity overall index according to the aircraft index and the assembly industry load index, and judging whether the center of gravity overall index is within the envelope limit range of the aircraft. Whether the integral center-of-gravity index is within the envelope limiting range or not is observed in a visual mode, the problem of low efficiency caused by complex operation is avoided, the center-of-gravity limiting efficiency in the flight process can be improved, and the flight safety is improved.
Description
Technical Field
The invention relates to the field of aircraft control, in particular to a method and a device for limiting the gravity center of an aircraft.
Background
When an aircraft is in a flying process, a pilot needs to constantly pay attention to whether a flying index is normal, for example, a gravity center related index is particularly important to flying safety, the aircraft can safely fly only when the gravity center is in a reasonable range, the gravity center of the aircraft moves forwards or backwards, and the flying performance can also change correspondingly, so that when the aircraft runs, the gravity center needs to be calculated in real time according to a loading condition and whether the aircraft is in the safe range, but the existing gravity center limiting condition judgment is complex, the calculation process is time-consuming, and the gravity center limiting condition of the aircraft cannot be judged subjectively and conveniently, and therefore an intuitive aircraft gravity center limiting method needs to be provided.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides an aircraft gravity center limiting method which can intuitively judge whether the real-time aircraft gravity center is within a safety limiting range.
In a first aspect, an embodiment of the present invention provides a: a method of aircraft center of gravity limiting, comprising:
displaying points of the aircraft in a coordinate system;
calculating an assembly industry load index, the assembly industry load index comprising: aircraft index, personnel supply index, business load index, fuel index;
and calculating to obtain a gravity center overall index according to the assembly industry load index, and judging whether the gravity center overall index is within the envelope limit range of the aircraft.
Further, the coordinate system includes: the X-axis is consistent with the advancing direction of the aircraft, the y-axis is vertical to the advancing direction of the aircraft in a horizontal plane, and the z-axis is perpendicular to the X-axis and the y-axis and is orthogonal to the X-axis and the y-axis.
Further, the formula for calculating the assembly industry load index is represented as:
wherein index represents an assembly industry load index, W represents weight, B a Sta, C, K represent constants, respectively.
Further, when the staff-supply index is calculated, the barycentric coordinate is calculated based on the position coordinates of the staff or the supply.
Further, when the fuel oil is liquid fuel oil, the fuel oil is converted into volume according to weight when the fuel index is calculated, and the barycentric coordinate is obtained through calculation according to the volume.
Further, the envelope limit is formed by connecting inflection point coordinates of the envelope gravity center limit.
Further, the assembly industry load indexes are added to obtain the gravity center integral index.
In a second aspect, the present invention also provides an aircraft center of gravity limiting device comprising:
coordinate system representation module: for displaying points of the aircraft in a coordinate system;
an index calculation module: for calculating an assembly industry load index, the assembly industry load index comprising: aircraft index, personnel supply index, service load index, fuel index;
a center of gravity limiting module: and the center of gravity overall index is calculated according to the assembly industry load index, and whether the center of gravity overall index is within the envelope limit range of the aircraft is judged.
In a third aspect, the present invention provides an aircraft center of gravity limiting apparatus comprising:
at least one processor, and a memory communicatively coupled to the at least one processor;
wherein the processor is adapted to perform the method of any one of the first aspect by invoking a computer program stored in the memory.
In a fourth aspect, the invention provides a computer-readable storage medium having stored thereon computer-executable instructions for causing a computer to perform the method of any one of the first aspects.
The invention has the beneficial effects that:
the invention calculates the aircraft index and the assembly industry load index by displaying the points of the aircraft in a coordinate system, wherein the assembly industry load index comprises the following components: and calculating the center of gravity overall index according to the aircraft index and the assembly industry load index, and judging whether the center of gravity overall index is within the envelope limit range of the aircraft. Whether the integral center-of-gravity index is within the envelope limiting range or not is observed in a visual mode, the problem of low efficiency caused by complex operation is avoided, the center-of-gravity limiting efficiency in the flight process can be improved, and the flight safety is improved.
Drawings
FIG. 1 is a schematic flow chart diagram illustrating one embodiment of a method for limiting the center of gravity of an aircraft in accordance with an embodiment of the present invention;
FIG. 2 is a schematic representation of a coordinate system of an embodiment of a method for limiting the center of gravity of an aircraft in accordance with an embodiment of the present invention;
fig. 3 is a block diagram of an embodiment of the device for limiting the center of gravity of an aircraft according to the embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
The first embodiment is as follows:
an embodiment of the present invention provides an aircraft center of gravity limiting method, and fig. 1 is a flowchart illustrating an implementation of the aircraft center of gravity limiting method according to the embodiment of the present invention, as shown in fig. 1, the method includes the following steps:
s1: displaying points of the aircraft in a coordinate system;
s2: calculating an assembly industry load index, wherein the assembly industry load index comprises: aircraft index, personnel supply index, service load index, fuel index;
s3: and calculating according to the assembly industry load index to obtain a gravity center integral index, and judging whether the gravity center integral index is within the envelope limit range of the aircraft.
Specifically, in step S1, as shown in fig. 2, a schematic diagram of the coordinate system of the present embodiment is shown. The coordinate system includes: the X-axis is consistent with the advancing direction of the aircraft, the Y-axis is vertical to the advancing direction of the aircraft on the horizontal plane, the Z-axis is vertical to the X-axis and the Y-axis and is orthogonal to the X-axis and the Y-axis, and the purpose of establishing a coordinate system is to describe the position of the aircraft space, divide each coordinate axis into small intervals according to the forward direction of the coordinate axis, and optionally divide the coordinate axes according to inches. Specific coordinates of each point on the aircraft can be given, the coordinate points are represented as (X, Y and Z), the loading position on the aircraft is described according to a coordinate system, three coordinate axis values of each position are obtained, the specific loading position is defined, and subsequent calculation is facilitated.
In step S2, the formula for calculating the assembly industry load index is expressed as:
wherein index represents an assembly industry load index, W represents weight, B a Sta, C, K represent constants (which may be changed according to actual requirements), specifically:
1) The aircraft index is an aircraft empty weight index, namely an index when the aircraft is unloaded, and is related to the aircraft according to the formula, and the aircraft belongs to a fixed value, and the related index is provided when the aircraft leaves a factory.
2) The personnel supply index means that corresponding weight and gravity center coordinates are calculated according to the seats of the personnel or the placing positions of supplies, the mode of calculating one by one and then overlapping can be adopted, and the personnel supply index can be obtained by calculating the overall weight and the relative gravity center position through overall analysis.
3) The industry load index refers to a corresponding industry load index obtained by calculation according to the assembly position of the weight of the assembly industry load of the aircraft, and as mentioned above, the industry load index can be obtained by adopting a mode of calculating one by one and then superposing, or by calculating the overall weight and the relative gravity center position through overall analysis.
4) The fuel oil in the fuel index is divided into two types: the fuel index calculation method comprises the steps that solid fuel oil and liquid fuel oil can be directly used for calculating the fuel index according to the formula, when the fuel oil is the liquid fuel oil, the liquid fuel oil is stored in a fuel bin, and the maximum loading capacity and the volume of the fuel bin belong to the prior data which can be obtained, so that the liquid fuel oil can be converted into the volume occupying the fuel bin according to the weight, the corresponding gravity center coordinate is obtained through calculation according to the occupied volume, and the fuel index is obtained according to the formula.
And step S3, adding the obtained various assembly industry load indexes one by one to obtain a gravity center integral index for judging gravity center limitation, wherein the specific method is to judge whether the gravity center integral index is in the envelope limitation range of the aircraft, if the gravity center integral index is in the envelope limitation range, the gravity center limitation condition is met, and the envelope limitation is an area formed by connecting maintenance envelope inflection points into envelope limitation.
The method is characterized in that different aircraft models have different gravity envelopes and are composed of maximum gliding weight, maximum takeoff weight, maximum landing weight, maximum fuel weight and corresponding gravity center limits during flying, a flight manual of the aircraft has a series of envelope inflection points formed by mutual influence and mutual restriction according to factors such as loading capacity, structural strength, stability operating characteristics and aircraft performance during flying of the aircraft of the model, and the gravity center limits are closed circles and are called envelope limits. Whether the real-time gravity center is in a safety range or not is judged by visually comparing the gravity center integral index obtained by calculation with the envelope limit, and the calculation efficiency and the flight safety are improved.
Further, when the aircraft has different envelope limits in different flight states, envelope switching can be performed as required.
Example two:
the present embodiment provides an aircraft center of gravity limiting device, configured to execute the method according to the first embodiment, as shown in fig. 3, which is a structural block diagram of the aircraft center of gravity limiting device according to the present embodiment, and includes:
coordinate system representation module 100: for displaying points of the aircraft in a coordinate system;
the index calculation module 200: for calculating an assembly industry load index, the assembly industry load index comprising: aircraft index, personnel supply index, business load index, fuel index;
center of gravity limiting module 300: and the center-of-gravity integral index is obtained by calculation according to the assembly industry load index, and whether the center-of-gravity integral index is within the envelope limit range of the aircraft is judged.
The specific details of the aircraft center of gravity limiting device module in the above description have been described in detail in the embodiment, which is a corresponding aircraft center of gravity limiting method, and therefore, the details are not described herein again.
In addition, the present invention also provides an aircraft center of gravity limiting device comprising:
at least one processor, and a memory communicatively coupled to the at least one processor;
wherein the processor is configured to perform the method of embodiment one by invoking a computer program stored in the memory. A computer program, i.e. a program code for causing an aircraft center of gravity limiting device to carry out the steps of the aircraft center of gravity limiting method as described in the section of the above embodiments of the present description, when the program code is run on the aircraft center of gravity limiting device.
In addition, the present invention also provides a computer-readable storage medium storing computer-executable instructions for causing a computer to perform the method according to the first embodiment.
The invention calculates the aircraft index and the assembly industry load index by displaying the points of the aircraft in a coordinate system, wherein the assembly industry load index comprises the following components: and calculating the center of gravity overall index according to the aircraft index and the assembly industry load index, and judging whether the center of gravity overall index is within the envelope limit range of the aircraft. Whether the integral center of gravity index is within the envelope limiting range or not is observed in an intuitive mode, the problem of low efficiency caused by complex operation is avoided, the center of gravity limiting efficiency in the flight process can be improved, and the flight safety is improved.
The above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, although the present invention is described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (7)
1. A method of limiting the center of gravity of an aircraft, comprising:
displaying points of the aircraft in a coordinate system;
calculating an assembly industry load index, the assembly industry load index comprising: aircraft index, personnel supply index, service load index, fuel index;
adding the assembly industry load indexes to obtain a gravity center integral index;
judging whether the center of gravity integral index is within the envelope limit range of the aircraft;
the formula for calculating the assembly industry load index is represented as follows:
wherein index represents an assembly industry load index, W represents weight, B a Denote barycentric coordinates, ref.sta, C, K denote constants, respectively;
the coordinate system includes: the X-axis is consistent with the advancing direction of the aircraft, the y-axis is vertical to the advancing direction of the aircraft in a horizontal plane, and the z-axis is perpendicular to the X-axis and the y-axis and is orthogonal to the X-axis and the y-axis.
2. The aircraft center of gravity limiting method of claim 1, wherein said center of gravity coordinates are calculated from position coordinates of personnel or supplies when calculating said personnel supply index.
3. The aircraft center of gravity limiting method of claim 1, wherein when the fuel is liquid fuel, said fuel index is calculated by converting said fuel by weight into a volume, and said center of gravity coordinate is calculated from said volume.
4. The aircraft center of gravity limiting method according to claim 1, wherein the envelope limit is formed by connecting inflection coordinates of the envelope center of gravity limit.
5. An aircraft center of gravity limiting device to which an aircraft center of gravity limiting method according to any one of claims 1 to 4 is applied, comprising:
coordinate system representation module: for displaying points of the aircraft in a coordinate system;
an index calculation module: for calculating an assembly industry load index, the assembly industry load index comprising: aircraft index, personnel supply index, business load index, fuel index;
a center of gravity limiting module: and the center of gravity overall index is calculated according to the assembly industry load index, and whether the center of gravity overall index is within the envelope limit range of the aircraft is judged.
6. An aircraft center of gravity limiting apparatus, comprising:
at least one processor; and a memory communicatively coupled to the at least one processor;
wherein the processor is adapted to perform the method of any one of claims 1 to 4 by invoking a computer program stored in the memory.
7. A computer-readable storage medium having computer-executable instructions stored thereon for causing a computer to perform the method of any one of claims 1 to 4.
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| CN201911157157.4A CN110901898B (en) | 2019-11-22 | 2019-11-22 | Aircraft gravity center limiting method and device |
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| CN115147023B (en) * | 2022-09-05 | 2022-12-20 | 中国民航信息网络股份有限公司 | Method and device for estimating gravity center of flight passenger |
| CN115204526B (en) * | 2022-09-14 | 2022-12-20 | 中国民航信息网络股份有限公司 | Flight fuel data acquisition and processing method, device and computer readable medium |
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| WO2002038444A2 (en) * | 2000-11-08 | 2002-05-16 | Toyota Motor Sales, U.S.A., Inc. | Methods and apparatus for automated flight preparation |
| CN103295177B (en) * | 2012-02-28 | 2016-04-20 | 杨光 | The remote centralized stowage method of collecting and distributing type shipping aviation and system |
| US9361486B2 (en) * | 2013-11-25 | 2016-06-07 | AeroData, Inc. | Determining a profile for an aircraft prior to flight using a fuel vector and uncertainty bands |
| CN105527955B (en) * | 2014-09-28 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Aircraft Quality characteristics modeling method |
| CN108069047B (en) * | 2017-12-01 | 2021-03-23 | 中国直升机设计研究所 | Method for controlling helicopter to use gravity center envelope |
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